Geometric description of a rotor blade

ABSTRACT

The invention is entirely in keeping with the industry of renewable energies, particularly those using kinetic energy from fluids. The invention comprises the non-conventional design of the shape or geometry of a rotor blade, such rotor being or not being coupled to a machine which generates power from the transformation of kinetic energy that a fluid in movement has. The fundamental purpose of the design is to improve the efficiency in which fluid kinetic energy is transformed, thus being able to obtain better power coefficient values and therefore better performance when generating power. Said rotor must have as a minimum two (2) blades (e) for the operation thereof and is primarily designed for wind power generation applications.

1. FIELD OF THE INVENTION

The present invention refers to renewable energy generation, particularly those taking advantage of fluid kinetic energy. The present invention refers more specifically to the non-conventional design of the shape of a rotor blade belonging to a machine which generates power from the transformation of kinetic energy found in moving fluids.

2. DESCRIPTION OF PRIOR ART

The wind power generation industry is currently searching for technologies which will make the power generation process more efficient and therefore focus their efforts into researching areas such as blade development having more efficient shapes allowing to better capture wind energy. This leads to innovation in specific issues such as aerodynamic improvements, the use of novel materials, control systems and blade manufacturing methodologies, the former being the work niche of the present invention.

To date, there are developments and documents which may be included within the category in which the present invention is found, given their result are non-conventional blade shapes; however, its operative improvement lies in completely different features. US2007/0013194A1 describes a non-conventional shape whose geometrical purpose is to reduce the aerodynamic noise generated by the rotor during operation and the purpose of the curvature in the invention is geared towards reducing the rotor's diameter given it prompts more effective kinetic energy capture from fluid by having a greater aerodynamic area. US2011/0070094 A1 describes an invention whose shape possesses a curvature which under principles different than aerodynamic forces, such as area reduction and Newton's third law of action reaction, prompt rotational blade movement, in addition, its cross-section is generated by the constant thickness sheet which channels fluid within the concave surface, in contrast to the cross-section of the present invention which uses a variable aerodynamic profile as a function of taking advantage of fluid-dynamic forces generated once the fluid passes through the inferior and superior zone of the profile. Other documents associated to the non-conventional blade category are CN101846042A and JP2010261431A, which have no similarity whatsoever with the operation or disposition of the present invention, and whose only relationship with the present invention lies in the implementation of non-conventional blade shapes of wind power generators.

The present invention comprises a solution to some of the problems and needs of the low-scale wind power generation industry, wherein current worldwide equipment installed offer in their vast majority efficiencies ranging anywhere between 20 to 30%; said value expected to be increased with new technologies and design methodologies. The present invention is directed precisely to increase said efficiency, reaching efficiency values between 45 and 55%.

3. BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 illustrates a preferred embodiment of the blade and the direction wherein the fluid is moving in the present invention.

FIG. 2 illustrates an overall three-dimensional view of the blade and its primary neutral axis included in plane P.

FIG. 3 illustrates a detailed view of the first section with its respective bending radius.

FIG. 4 illustrates a two-dimensional view of airfoil PA_(ij).

FIG. 5 illustrates a two-dimensional view of the blade's first section along the {right arrow over (X)}₀{right arrow over (Z)}₀ plane.

FIG. 6 illustrates a detailed three-dimensional view of the blade's cross-section.

FIG. 7 illustrates a three-dimensional view of the blade's second section.

FIG. 8 illustrates a three-dimensional of the blade's third section.

FIG. 9 illustrates a three-dimensional view of the configuration in a preferred embodiment for the wind power generation system.

FIG. 10 illustrates a view of the fluid flow through the wind power generation system.

FIG. 11 illustrates the direction of rotation of the wind power generation system.

4. BRIEF DESCRIPTION OF THE INVENTION

The present invention discloses a blade for the generation of electrical energy stemming from the transformation of kinetic energy of a fluid, in rotational movement. Said rotational movement is moved to a central horizontal axis which may be coupled to an electric generator. Said horizontal axis is found defined by a Cartesian axis {right arrow over (Z)}₀ which together with Cartesian axes {right arrow over (X)}₀ {right arrow over (Y)}₀, form a global orthogonal framework of clearance planes.

Blade (e) has a particular geometrical shape which extends along axis {right arrow over (Z)}₀, moving away thereof as it continues to develop, and is limited longitudinally by Root (a) and Tip (b), whose connection is obtained by a series of sectional and constant curvatures called Sectional Neutral Axes En_(i) which generate all together a continuous or discontinuous primary curvature called Primary Neutral Axis En. Cross-sectionally, it is found limited by an Leading Edge (f) and an Trailing Edge (d), which when joined by one or two continuous curves which connect several points, amongst them the point corresponding to the leading edge and the trailing edge, form an Aerodynamic Profile/Airfoil PA_(ij) having a variable or constant thickness. The volume defined by these five borders (Root, Tip, Leading Edge, Trailing Edge, Airfoil) generates the shape of the blade.

The main geometrical feature of the blade is the curvature, defined by the Sectional Neutral Axes En_(i), which as mentioned above, when joined form the Primary Neutral Axis En whose curvature length is given by L, which may lie in the range of 0.01 m≧L≧30 m. In order to create this curvature, a series of points Pc_(ij) are joined; these points are constructed along the bottom curve describing airfoil PA_(ij), at a distance of c/4 from the leading edge point, c being the length of the airfoil cord.

Said Primary Neutral Axis En is included within plane P, which coincides with the {right arrow over (X)}₀{right arrow over (Z)}₀ plane. The initial point of Primary Neutral Axis En, the root, is located by an auxiliary reference framework {right arrow over (X)}₁{right arrow over (Y)}₁{right arrow over (Z)}₁; initiating at the intersection of plane {right arrow over (X)}₁{right arrow over (Y)}₁ which is parallel to plane {right arrow over (X)}₀{right arrow over (Y)}₀ and perpendicular to the rotation axis {right arrow over (Z)}₀; with plane {right arrow over (Y)}₁{right arrow over (Z)}₁ which is parallel to plane {right arrow over (Y)}₀{right arrow over (Z)}₀; and to plane {right arrow over (X)}₁{right arrow over (Z)}₁ which coincides with plane {right arrow over (X)}₀{right arrow over (Z)}₀ and thus with plane P, if the preferred embodiment is had. This intersection point 1 between the auxiliary planes, is where Primary Neutral Axis En begins and is also identified as the initial point of the first of three division sections of En.

The first section of division L₁ corresponds, in the blade's preferred embodiment, to 20% of L; however, it may range between 0.15*L≧L₁≧0.25*L. This section is limited by points 1 and 2, whereby the latter is found towards the end of the length of L₁ over Sectional Neutral Axis En₁. The second division section is defined by L₂; this section begins at point 2 and ends at point 3 located over Sectional Neutral Axis En₂, in accordance to the preferred embodiment, this section has a length corresponding to 40% of L, but however it may vary between 0.3*L≧L₂≧0.5*L. The last division section of the blade corresponds to L₃ and is limited by points 3 and 4; its length, as defined in the preferred embodiment is 40% of L, and like the other sections has a length between 0.3*L≧L₃≧0.5*L. The different arches defining each one of these sections, are tangents at each one of the connection points, i.e., section L₁ is tangent to section L₂ at point 2 and section L₂ is tangent to section L₃ at point 3.

The shape of the blade undergoes a series of variations in its cross-section, which develop along the Primary Neutral Axis En from point 1 to point 4 and which like curvature L, these variations are analyzed at the same three sections L₁L₂L₃. The first variation evidenced is the length of the cross-section, seen as the decrease or increase of the length of cord c of airfoil PA_(ij). The length of said cross section is bound by ranges 0,05*L≧c₁₁≧0,3*L and 0,01*L≧c₃₃≧0,3*L, for aerodynamic profiles located at the root and tip of the blade, respectively.

The second geometrical variation corresponds to a torsion which varies along Primary Neutral Axis En from point 1 to point 4 and which like curvature L, these variations are analyzed at the same three sections L₁L₂L₃. This torsion is measured as a function of angle α_(ij) which is formed between cord c of each PA_(ij) profile and a perpendicular axis u to plane P which intersects Primary Neutral Axis En at point Pc_(ij). This angle way be both positive as well as negative, having angle 0° as an inflection point, which is formed when the u axis is parallel to the c cord. A positive angle exists when said angle grows clockwise and negative when counter-clockwise.

At the root of the blade, the torsion angle may range between the following values, −38°≧α_(i)≧148° and the tip's torsion angle may range between −46°≧α_(i)≧40°. However, in the preferred embodiment the torsion is found between −31°≧α_(i)≧30° and −44°≧α_(i)≧16° for the root and tip, respectively.

For a configuration with greater performance, said torsion lies in the following ranges: 5°≧α_(i)≧25° and −5°≧α_(i)≧15°, for the root and tip respectively.

5. DETAILED DESCRIPTION OF THE INVENTION

The present invention discloses a blade for electric power generation stemming from the transformation of a fluid's kinetic energy into rotational movement, wherein the capacity of kinetic energy transformation into rotation movement is directly correlated to the effective contact area between the blade and air flow. The present invention provides an increase of said effective area in contrast to a conventional flat blade, given its curved shape allows that for an equal effective diameter, a greater contact surface can be provided and thus a greater amount of energy generated.

In addition, the blade's curvature herein allows for the kinetic energy found in the fluid's flow to be used in a greater proportion in contrast to that obtained using a conventional mainly flat-shaped blade. The above due to that air flow impacting the blade does not do so perpendicularly as usually happens in conventional designs, wherein the greater part of the flow energy is transformed into drag forces associated to the pressure of impact, but instead, the flow impacting the blade does so at an angle with respect to the blade allowing for the flow to acquire velocity components which are used in kinetic energy transformation of the flow into rotational movement.

The present invention discloses a blade for the generation of electrical power from the transformation of a fluid's kinetic energy into rotation movement. Said rotational movement is moved to a central horizontal axis which may be coupled to an electrical generator. This rotation horizontal axis is defined by a Cartesian axis {right arrow over (Z)}₀ which together with Cartesian axes {right arrow over (X)}₀ {right arrow over (Y)}₀, form a global orthogonal framework of clearance planes.

Making reference to FIG. 1 and FIG. 2, an embodiment of blade (e) of the present invention is shown, having a particular geometrical shape which extends along axis {right arrow over (Z)}₀, moving away thereof as it continues to develop, and is limited longitudinally by Root (a) and Tip (b), whose connection is obtained by a series of sectional and constant curvatures called Sectional Neutral Axes En_(i) which generate all together a continuous or discontinuous primary curvature called Primary Neutral Axis En.

Given the curvature of the Primary Neutral Axis En may be continuous or discontinuous, it is necessary, for the latter, divide its length in different sections which allows to characterize the invention in continuous curvatures or Sectional Neutral Axes En_(i). The number of sections is one (1) for continuous Primary Neutral Axes En and at least two (2) for discontinuous Primary Neutral Axes En, wherein L₂ comprises 50% of L and L₃ the other 50%. However, for the preferred embodiment, the blade is divided into three (3) sections represented by Sectional Neutral Axes En₁, En₂, En₃ found between points 1 −2; 2 −3; and 3 −4.

The first section En₁ starts at point 1, has a preferred length of L₁=0, 2*L and ends at point 2. This section corresponds to the root zone, where the blade is attached to the horizontal rotation axis. En₁ is a constant curve obtained from the polynomial interpolation of various points. Its constant bending radius Rp₁ has a focus located at plane P at a preferred distance of Rp₁=4*L₁; said bending radius can range between 1, 3*L₁≧Rp₁≧57*L₁. At point 1 and perpendicular to curve En₁, plane A is located and having an angle {right arrow over (X)}{right arrow over (Y)}°₁ with plane {right arrow over (X)}₁{right arrow over (Y)}₁, said angle ranging between 0°≧X{right arrow over (Y)}°₁≧90°. However, its preferred value ranging from 0°≧{right arrow over (X)}{right arrow over (Y)}°₁≧40° and its greatest efficiency range between 10°≧{right arrow over (X)}{right arrow over (Y)}°₁≧20°.

In FIG. 2, section En₁ is observed formed by at least three (3) cross-sections, whose geometrical shape is an airfoil PA_(ij), named PA₁₁, PA₁₂ y PA₁₃. Each one of these profiles are found on a plane perpendicular to En₁, the first plane A corresponds to profile PA₁₁ and located at point 1; the second plane B belongs to profile PA₁₂ and its location is at sectional neutral axis En₁ at an intermediate point between 1 and 2; at the third plane D, the airfoil PA₁₃ is found and is located at point 2.

Making reference to FIG. 3, which illustrates a detailed view of the first section showing the respective bending radius, it may be noted that on the bottom curve of airfoils PA₁₁, PA₁₂ y PA₁₃, called intratwo, points Pc₁₁, Pc₁₂ y Pc₁₃ are located, respectively. These points are located at a distance of c/4 from the leading edge and by joining them in an arch containing them, the Sectional Neutral Axis En₁ is obtained.

If a material extrusion is generated which follows the path described by the En₁ curve and said path conserves the shape of multiple cross-sections in its sweep (airfoils), the solid having the geometric shape of the invention is generated at the root zone.

Using the configuration of greatest performance, this first section demonstrates a progressive change in its transverse length; this is due to the fact that cord c suffers an increase in size as it moves away from the beginning of the En₁ curve at point 1, where the cord shows values of 0,082*L, 0,092*L, 0,099*L, for profiles PA₁₁, PA₁₂ and PA₁₃, respectively.

However, this section may demonstrate progressive or regressive changes or a combination thereof in cord length, provided they are within the following ranges: 0,05*L≧c₁₁≧0, 3*L; 0,046*L≧c₁₂≧0,3*L; 0,042*L≧c₁₃≧0,3*L.

Making reference to FIG. 4, a two-dimensional view of airfoils PA_(ij) is shown, wherein each aerodynamic profile PA_(ij) making part of section En₁ has an inclination angle α_(ij) (α₁₁α₁₂α₁₃) formed between cord c of each PA_(ij) profile and u axis. The first airfoil in this section may lie between the following values, −30°≧α₁₁≧120° and the profile torsion angle and point 2 may lie between −34°≧α₁₃≧105°. However, in the preferred embodiment, said torsion is limited by the following ranges 5°≧α_(i)≧25° and 1°≧α_(i)≧19°, for profiles α₁₁ and α₁₃, respectively (also see FIG. 5).

In FIG. 7, it may be noted that second section En₂ initiates at point 2, has a preferred length of L₂=0, 4*L and ends at point 3. This section corresponds to the internal zone, wherein the greatest percentage of aerodynamic forces that the blade generates in its entirety are concentrated. En₂ is a constant curve obtained from the polynomial interpolation of several points. Its constant bending radius Rp₂ has a focus located on plane P at a preferred distance of Rp₂=2*L₂; this bending radius may be in the following range: 1*L₂≧Rp₂≧5*L₂.

Section En₂ is made up of at least three (3) equidistant cross-sections, whose geometric shape is an airfoil PA_(ij), called PA₂₁, PA₂₂ y PA₂₃. Each one of these profiles is found on a plane perpendicular to En₂; the first plane E corresponds to profile PA₂₁ and is located at point 2; the second plane F corresponds to profile PA₂₂ and it is located on sectional neutral axis En₂ at an intermediate point between 2 and 3; airfoil PA₂₃ is located on plane G and is located on point 3.

On the bottom curve of airfoils PA₂₁, PA₂₂ and PA₂₃, called intratwo, points Pc₂₁, Pc₂₂ and Pc₂₃ are located, respectively. These points are at a distance of c/4 from the leading edge and by joining them in an arch containing them, the Sectional Neutral Axis En₂ is obtained.

If the material extrusion used in the first section (root) is continued, i.e. following the path described by curve En₂ and maintaining the shape of the multiple cross-sections PA₂₁, PA₂₂ and PA₂₃ in its sweep, the solid having the geometric shape of the invention is generated in the internal zone of the blade.

This second section in contrast to the first shows two sectional changes in its configuration of greatest performance; the first being a progressive change in the length of cord c from point 2 up to near the central point of curvature En₂. This point, preferably located on plane F is considered the inflection point of the cord of the section's airfoils, since from it, cord c of the cross-sections describe a regressive behavior and its size begins to decrease until point 3. In accordance with this embodiment, the cord has a value of 0,099*L, 0,104*L, 0,094*L, for profiles PA₂₁, PA₂₂ and PA₂₃, respectively.

Nevertheless, this section may show progressive or regressive changes or combinations thereof in cord length, provided they are within the following ranges: 0,042*L≧c₂₁≧0,3*L; 0,034*L≧c₂₂≧0,3*L; 0,026*L≧c₂₃≧0,3*L.

Each airfoil PA_(ij) making part of section En₂ has an inclination angle α_(ij) (α₂₁α₂₂α₂₃) formed between cord c and each PA_(ij) profile and the u axis. The first airfoil of this section may lie within the following values, −34°≧α₂₁≧105° and the final profile torsion angle at point 3 may range between −41°≧α₂₃≧60°. However, in its configuration of greatest performance, said torsion is bound by the ranges 1°≧α_(i)≧19° and −5°≧α_(i)≧13°, for profiles α₂₁ and α₂₃, respectively.

The third section En₃ initiates at point 3, has a preferred length of L₃=0,4*L and ends at point 4. This section corresponds to the external zone, and here is where the greatest rotational velocity components are found, and therefore its inertia must be the least in order to reduce stresses; this is obtained by decreasing the size of the airfoils which make part of the section. En₃ is a constant curve obtained from the polynomial interpolation of various points. Its constant bending radius Rp₃ has a focus located at plane P at a preferred distance of Rp₃=5*L₃; said bending radius can range between 1*L₃≧Rp₃≧12*L₃.

Making reference to FIG. 8, section En₃ is shown which is made up of at least three (3) equidistant cross-sections, whose geometric shape is an airfoil PA_(ij), called PA₃₁, PA₃₂ y PA₃₃. Each one of these profiles is found on a plane perpendicular to En₃; the first plane H corresponds to profile PA₃₁ and is located at point 3; the second plane I corresponds to profile PA₃₂ and is located on sectional neutral axis En₃ at an intermediate point between 3 and 4; airfoil PA₃₃ is located on plane J and is located on point 4.

On the bottom curve of airfoils PA₃₁, PA₃₂ and PA₃₃, called intratwo, points Pc₃₁, Pc₃₂ and Pc₃₃ are located, respectively. These points are at a distance of c/4 from the leading edge and by joining them in an arch containing them, Sectional Neutral Axis En₃ is obtained.

Continuing with material extrusion of the second section, i.e. following the path described by curve En₃ and maintaining the shape of the multiple cross-sections (airfoils) during its sweep, the solid having the geometric shape of the invention is generated in the external zone.

This third and preferably last section, develops a regressive change in its transverse length for the embodiment of greatest performance; this is due to the fact that cord c decreases its size as it moves away from the beginning of curve En₃ at point 3. In accordance with this embodiment, the cord has a value of 0,094*L, 0,080*L, 0,070*L, for profiles PA₃₁, PA₃₂ and PA₃₃, respectively.

Nevertheless, this section may show progressive or regressive changes or combinations thereof in cord length, provided they are within the following ranges: 0,026*L≧c₃₁≧0,3*L; 0,018*L≧c₃₂≧0,3*L; 0,01*L≧c₃₃≧0,3*L.

Each airfoil PA_(ij) making part of section En₃ has an inclination angle α_(ij) (α₃₁α₃₂α₃₃) formed between cord c of each PA_(ij) profile and u axis. The first airfoil in this section may lie between the following values, −41°≧α₃₁≧60° and the profile torsion angle at point 4 may lie between −44°≧α₃₃≧16°. However, in its configuration of greatest performance, said torsion is limited by the following ranges 5°≧α_(i)≧13° and 5°≧α_(i)≧15°, for profiles α₃₁ and α₃₃, respectively.

The combination of bending radius ranges for sections Rp₁, Rp₂ and Rp₃ must be in such a manner that when the blade has its greatest curvature, a tangent line at point 4 must be at most perpendicular to rotation axis {right arrow over (Z)}₀.

Embodiment Example

In order to carry out the blade fluid dynamics testing, several tests were run using computer simulation. The following is information evidencing the invention's performance:

Operating conditions: sea-level

-   -   Numerical method used: Finite volumes     -   Simulator software used: Fluent (ANSYS).

The blades were designed in order to operate optimally both at low as well as high speeds with an optimal rotor tip speed ratio (TSR) of 6; i.e., the rotor must rotate at an RPM such that the tangential speed of the blade tip is 6 times the velocity of the fluid it faces.

The following graph shows the blade's Cp (coefficient of power) for different speeds and different TSR. This demonstrated that efficiencies (Cp) over 40% for TSR between 4 and 7 are obtained. However, the greatest efficiency is gained for TSR between 5 and 6, the range in which the system is calculated will operate, as demonstrated in the following graph. It is reminded that the maximum efficiency a rotor can achieve is 59.3%, which corresponds to the Betz limit which is 0.593.

The performance demonstrated above corresponds to one of the possible configurations whereby the invention may be constituted, mainly the preferred embodiment for a wind power generation system as shown by FIG. 9. This array comprises a total of three blades (e) radially placed at a 120° angle from each other, said blades (e) are fixed in the direction stated above by a support system (g); said support system (g) is attached to an electrical energy generating system having a rotation axis (h) (in the same location as imaginary rotation axis {right arrow over (Z)}₀) allowing for rotational movement of the blades (e) in the direction illustrated by the vectors (m); a shaft (j) located vertically which elevates the system up to a determined height, the electrical energy generating system is attached thereto which possesses a rotation axis (h) from which the support system (g) is attached which in turn holds the blades (e); a keel (i) attached to the shaft (j) which purpose is to cover the frontal zone of the system in order to smooth the fluid's flow (k) that impacts the blades (e); in this configuration of the preferred embodiment, said fluid (k) is air.

Making reference to FIGS. 10 and 11, the present invention's operation is shown under the configuration set forth above, comprising the transformation of linear kinetic energy possessed by fluid (k) in movement, in rotational movement (m) of the blades (e) when these are impacted by air. The rotation process begins when the air impacts the leading edge (f) and moves through the bottom and top surfaces comprising the airfoils PA_(ij) of blade (e), until arriving finally to the trailing edge (d). The air passing through the top zone acquires greater speed than the air passing through the bottom zone, thus generating a pressure differential on these surfaces, which finally translates in a lift force having a component in the rotation direction (m) thus generating torque with respect to the rotation axis (h).

The advantage offered by this invention with respect to prior art, is the capacity of transforming said kinetic energy in rotational movement which is directly correlated to the effective contact area between the blade (e) and the air flow (k); thus the invention presents an increase of said effective area in comparison to a conventional flat blade, this because of its curved shape which allows that for a same effective diameter, a greater contact surface can be made and therefore generating greater amount of energy.

As stated above, the curvature of blade (e) allows for kinetic energy possessed by the flow (k) of the fluid in movement to be used in greater proportion than that obtained using a conventional flat-shaped blade. The above is true given the air flow impacting the blade is not perpendicular as usually happens in conventional designs, wherein the greater part of the flow's energy is transformed into drag forces associated to impact pressure, and in contrast, the flow impacts blade (e) at an angle with respect to the blade (e) allowing for the flow to acquire speed components which are used in transforming flow kinetic energy in rotational movement (m).

It must be understood that the present invention is not found limited by the embodiments described and illustrated, since as shall be evident for those with skill in the art, variations and possible modifications exist that do not extend from the scope and spirit of the invention, which is only defined by the following claims. 

1. A blade for the generation of electrical energy, from the transformation of kinetic energy of a fluid in rotation movement of the blade, wherein said movement is transmitted to a rotation axis coupled to said blade located in an orthogonal framework of clearance planes [{right arrow over (X)}₀], [{right arrow over (Y)}₀] y [{right arrow over (Z)}₀], wherein the shape of said blade is characterized in that, it extends along axis [{right arrow over (Z)}₀], longitudinally bound by the root (a) and the tip (b), which connect through a series of neutral sectional axes [En_(i)] which generate a continuous or discontinuous Primary Neutral Axis [En]; it is transversely bound by the leading edge (f) and the trailing edge (d) which upon joining them by means of continuous curves comprise an airfoil [PA_(ij)]; the curvature of said blade (e) has a length L, which is between 0.01 m and 30 m, and is defined by neutral sectional axes [En_(i)], which when joined form the primary neutral axis [En], said curvature is formed by joining a series of points [Pc_(ij)], which are constructed over the bottom curve of the airfoil [PA_(ij)], at a distance of c/n from the leading edge point (f), where c is the cord length of the airfoil [PA_(ij)]; the Primary Neutral Axis [En] is included within plane [P], which coincides with the {right arrow over (X)}₀{right arrow over (Z)}₀ plane, wherein the initial point (1) of said Primary Neutral Axis [En], is at the root, at the intersection of plane {right arrow over (X)}₁ {right arrow over (Y)}₁ with plane {right arrow over (Y)}₁{right arrow over (Z)}₁; the blade (e) has at least one division section of [En] having a length [L_(n)]; and wherein the blade's shape has a variable cross section along the Primary Neutral Axis [En].
 2. (canceled)
 3. The blade (e) according to claim 1, characterized in that the blade (e) has three division sections wherein a first division section En₁ has a length L₁ limited to a range between 0.15*L≧L₁≧0.25*L; the second division section En₂ located over Sectional Neutral Axis En₂, and wherein said second section has a length L₂ limited to a range between 0.3*L≧L₂≧0.5*L; the third division section En₃ has a length L₃ and whose length L₃ is limited by the range between 0.3*L≧L₃≧0.5*L; section L₁ is tangent to section L₂ at the intersection point between section 1 and 2, and section L₂ is tangent to L₃ at its corresponding junction point.
 4. (canceled)
 5. The blade (e) in accordance to claim 1, characterized because the geometry of the blade has a variable cross section along the Primary Neutral Axis [En]; wherein a first variation the length of the cross-section is the change in length of the cord c of the airfoil PA_(ij); and wherein a second geometrical variation corresponds to a torsion which varies along the Primary Neutral Axis En, said second geometrical variation is measured as a function of angle α_(ij) formed between cord c of each airfoil PA_(ij) and an axis u perpendicular to plane P which intersects the Primary Neutral Axis En at point Pc_(ij), said angle ranges between −38°≧α_(i)≧148 at the root (a) and between −46°≧α_(i)≧40° at the tip (b).
 6. (canceled)
 7. (canceled)
 8. The blade (e) in accordance to claim 3, wherein the length of c is within the range of 0,05*L≧c₁₁≧0,3*L for the airfoil located at the root (a) and by the range 0,01*L≧c₃₃≧0,3*L for the airfoil located at the tip (b).
 9. (canceled)
 10. The blade (e) in accordance to claim 3, wherein L₁ at the first division section of the blade (e) is 20% of L, L₂ in the second division section of the blade (e) is 40% of L and L₃ in the third division section of the blade (e) is 40% of L.
 11. The blade (e) in accordance to claim 5, wherein said angle α_(ij) of the second geometric variation ranges between −31°≧α_(i)≧30° at the root (a) and between −44°≧α_(i)≧16 at the tip (b).
 12. The blade (e) in accordance to claim 5, wherein said angle α_(ij) of the second geometric variation ranges between 5°≧α_(i)≧25° at the root (a) and between −5°≧α_(i)≧15 at the tip (b).
 13. The blade (e) in accordance to claim 3, wherein the first division section En₁ corresponds to the root zone, from which the blade attaches to a horizontal rotation axis and which is an extrusion that follows the path described by the En₁ curve and which maintains throughout its sweep the shape of its airfoils, this root zone En₁ is a constant curve having a constant curvature radius Rp₁, preferably Rp₁=4*L₁, which has a focus located on plane P at a distance which ranges between 1, 3*L₁≧Rp₁≧57*L₁; at point 1 and perpendicular to the curve En₁, plane A is located providing angle {right arrow over (X)}{right arrow over (Y)}°₁ with plane {right arrow over (X)}₁{right arrow over (Y)}₁ in the range, 0°≧{right arrow over (X)}{right arrow over (Y)}°₁≧90°; said root zone En₁ is comprised of at least three (3) equidistant transverse sections PA₁₁, PA₁₂ and PA₁₃, whose geometrical shape is an airfoil PA_(ij), and wherein each of these airfoils is located on a plane perpendicular to En₁, the first plane A located at point 1 corresponds to airfoil PA₁₁; the second plane B located on the sectional neutral axis En₁ at an intermediate point between 1 and 2 belongs to the airfoil PA₁₂; and the third plane D located at point 2 corresponds to the airfoil PA₁₃; Sectional Neutral Axis En₁ corresponds to joining points Pc₁₁, Pc₁₂ and Pc₁₃ through an arc at a distance of c/4 from the leading edge and located on the bottom curve of airfoils PA₁₁, PA₁₂ and PA₁₃; the transverse length of said root zone provides progressive and regressive changes or combinations thereof through the cord length, ranging between 0,05*L≧c₁₁≧0,3*L; 0,046*L≧c₁₂≧0,3*L and 0,042*L≧c₁₃≧0,3*L; each airfoil PA_(ij) making part of section En₁ has an angle of inclination α_(ij) (α₁₁α₁₂α₁₃) formed between the cord c of each airfoil PA_(ij) and the u axis, wherein the first airfoil of root zone ranges between −30°≧α₁₁≧120° and the torsion angle airfoil at the end in point 2 ranges between −34°≧α₁₃≧105°.
 14. (canceled)
 15. The blade (e) in accordance to claim 13, wherein said angle {right arrow over (X)}{right arrow over (Y)}°₁ with plane {right arrow over (X)}₁{right arrow over (Y)}₁ ranges between 0°≧{right arrow over (X)}{right arrow over (Y)}°₁≧40°.
 16. The blade (e) in accordance to claim 15, wherein said angle {right arrow over (X)}{right arrow over (Y)}°₁ with plane {right arrow over (X)}₁{right arrow over (Y)}₁ ranges between 10°≧{right arrow over (X)}{right arrow over (Y)}°₁≧20°.
 17. The blade (e) in accordance to claim 13, wherein said transverse length of said root zone shows progressive change in its transverse length, wherein said cord c undergoes a size increase as it moves away from the beginning of curve En₁ at point 1, wherein the curve has a value of 0,082*L, 0,092*L, 0,099*L, for airfoils PA₁₁, PA₁₂ and PA₁₃, respectively.
 18. The blade (e) in accordance to claim 13, wherein the first airfoil of said root zone ranges between 5°≧α₁₁≧25° and the torsion angle of the final airfoil in point 2 ranges between 1°≧α₁₃≧19°.
 19. The blade (e) in accordance to claim 3, wherein the second division section En₂ corresponds to the internal zone which is an extrusion that follows the path described by the En₂ curve and which maintains throughout its sweep the shape of its airfoils PA₂₁, PA₂₂ and PA₂₃, this internal zone En₂ is a constant curve having a constant curvature radius Rp₂, preferably Rp₂=2*L₂, which has a focus located in plane P at a distance which ranges between 1*L₂≧Rp₂≧5*L₂; said internal zone En₂ is comprised for at least three (3) equidistant transverse sections PA₂₁, PA₂₂ and PA₂₃, whose geometrical shape is an airfoil PA_(ij), and wherein each of these airfoils is located on a plane perpendicular to En₂, the first plane E located at point 2 corresponds to airfoil PA₂₁; the second plane F located on the sectional neutral axis En₂ at an intermediate point between 2 and 3 belongs to the airfoil PA₂₂; and the third plane G located at point 3 corresponds to the airfoil PA₂₃; Sectional Neutral Axis En₂ corresponds to joining points Pc₂₁, Pc₂₂ and Pc₂₃ through an arc at a distance of c/4 from the leading edge and located on the bottom curve of airfoils PA₁₁, PA₁₂ and PA₁₃; the transverse length of this internal zone provides progressive and regressive changes or combinations through the chord length, with the ranges 0,042*L≧c₂₁≧0,3*L, 0,034*L≧c₂₂≧0,3*L and 0,026*L≧c₂₃≧0,3*L; each airfoil PA_(ij) that is part of section En₂ has an angle of inclination α₁₁ (α₂₁α₂₂α₂₃) formed between the cord c of each airfoil PA_(ij) and the u axis, wherein the first airfoil of said internal zone ranges between −34°≧α₂₁≧105° and the torsion angle airfoil at the end in point 3 ranges between −41°≧α₁₃≧60°.
 20. (canceled)
 21. The blade (e) in accordance to claim 13, wherein said transverse length of said internal zone shows two sectional changes; the first is a progressive change in the length of cord c from point 2 up to an inflection point at the middle of curvature En₂, said inflection point is located on plane F; and the second sectional change is a regressive change of cord c of the cross-sections, which decrease until point 3, said cord c having a value of 0,099*L, 0,104*L, 0,094*L, for airfoils PA₂₁, PA₂₂ and PA₂₃, respectively.
 22. The blade (e) in accordance to claim 18, wherein the first airfoil of said zone ranges between 1°≧α₂₁≧19° and the torsion angle of the final airfoil in point 3 ranges between −5°≧α₂₃≧13°.
 23. The blade (e) in accordance to claim 3, wherein the third division section En₃ corresponds to the external zone which is an extrusion following the path described by the En₃ curve and which maintains throughout the sweep the shape of its airfoils PA₃₁, PA₃₂ and PA₃₃, said external zone En₃ is a constant curve having a constant curvature radius Rp₃, preferably Rp₃=5*L₃, which has a focus located on plane P at a distance which ranges between 1*L₃≧Rp₃≧12*L₃; said external zone En₃ is comprised for at least three (3) equidistant transverse sections PA₃₁, PA₃₂ and PA₃₃, whose geometrical shape is an airfoil PA_(ij), and wherein each of these airfoils is located on a plane perpendicular to En₃, the first plane H located at point 3 corresponds to airfoil PA₃₁; the second plane I located on the sectional neutral axis En₃ at an intermediate point between 3 and 4 belongs to the airfoil PA₃₂; and the third plane J located at point 4 corresponds to the airfoil PA₃₃; Sectional Neutral Axis En₃ corresponds to joining points Pc₃₁, Pc₃₂ and Pc₃₃ through an arc at a distance of c/4 from the leading edge and located on the bottom curve of airfoils PA₃₁, PA₃₂ and PA₃₃; the transverse length of this external zone provides progressive and regressive changes or combinations through the cord length, in the ranges 0,026*L≧c₃₁≧0,3*L, 0,018*L≧c₃₂≧0,3*L, and 0,01*L≧c₃₃≧0,3*L; each airfoil PA_(ij) that is part of section En₃ has an angle of inclination α_(g) (α₃₁α₃₂α₃₃) formed between the chord c of each airfoil PA_(ij) and the u axis, wherein the first airfoil of this internal zone ranges between −41°≧α₃₁≧60° and the torsion angle airfoil at the end in point 4 ranges between −44°≧α₃₃≧16°.
 24. (canceled)
 25. The blade (e) in accordance to claim 13, wherein said transverse length of said external zone shows a regressive change of cord c as it moves away from the beginning of curve En₃ at point 3, said cord c having a value of 0,094*L, 0,080*L, 0,070*L, for airfoils PA₃₁, PA₃₂ and PA₃₃, respectively.
 26. The blade (e) in accordance to claim 19, wherein the first airfoil of said zone ranges between −5°≧α₃₁≧13° and the torsion angle of the final airfoil in point 4 ranges between −5°≧α₃₃≧15°.
 27. The blade (e) in accordance to claim 1, wherein a tangent line at point 4 is at most, perpendicular to the rotation axis {right arrow over (Z)}₀ when the blade shows its greatest curvature and in accordance with the combination of curvature radius ranges of sections Rp₁, Rp₂ and Rp₃. 